Instrument landing equipment



Jan. 25, 1944. E. N. D1NG'LEY,JR I 2,340,282.

INSTRUMENT LANDZIIZNG EQUIPMENT Filed Feb. 21, 1938 4 Sheets-Sheet 1 ZS Q 28 v 30 E0 lTc-mll Tic-bi v INVENTOR H l O EDWARD N. omeLe JR.

w, ATTORNEY .Jan. 25,1944. v N DINGLEY, JR I 3 5 INSTRUMENT LANDING EQUIPMENT Filed Feb. 21, 1938 4 Sheets-Sheet 5 INVENTOR' EDWARD N. DINGLEY JR.

ATTORNEY.

Jan. 25, 1944. E. N. DINGLEY, JR 2,340,282

INSTRUMENT LANDING EQUIPMENT 7 Filed Feb. 21, 1938 4 Sheeis-Sheet 4 AWL/nae 15 20 4s INVENTOR- EDWARD N. DINGLEY JR.

ATTORNEY craft, the exact position of the craftand by reference to the that may beused of thecurrents from the coils;-

I the use of a vertical and a horilight to show when the off course;

' .ments that may be used in single cable of Fig.

Patentcd'Jan. 25, 1944 1 UNITED STATE.

s PATENT OFFICE c INSTRUMENT LANDING EQUIPMENT V Edward N. Dingley, Jr., Arlington, va. Application ebruary 21, 1938, Serial No. 191,735

(Granted under the. act of March 3, 1883, as

amended April 30, 1928; 370 0. G. 757) 23 Claims.

My invention relates broadly to instrument landing systems by means of which aircraft may be guided safely along a predeterminedlandmg glide path and caused to land properly at a designated point at times of. low or zero visibility.

My. invention relatees chiefly to circuit arrangements in which the relative magnitude of two electromagnetic fields produced on or near the surface of the earth is indicated visually at a point in space occupied by an aircraft.

One of the objects of my invention is to provide and'instrum'ent landing system by means of which a predetermined glide path is fixed in space regardless of the variations of ground conductivity normally encountered.

Another object of my invention is to provide a means for establishing and maintaining under all conditions a glide path in space having any desired curvature or configuration;

Still another object of my invention is to provide equipment suitable for installation on the ground and other equipment suitable for installation in aircraft which will at all times make producing the magnetic field.

Fig. 17 shows diagrammatically an oscillator connectable to the landing 'system for calibration purposes;

Fig. 18 is a schematic diagram of-a cathode ray tube connected to, be used as an indicator,

, Fig. 1 represents one embodiment 'of my inventiorr'wherein the horizontal cables I and 2 are laid on, under, or above the. surface of the earth v on each side of and equally spaced from a landing runway 24. The cables I and 2 are interconnected at intervals throughout their length by the cables 6 in series with each of which there possible the determin-atiOn by the pilot of therelative to the predetermined glide path.

Other and further objects of my invention will be understood from the following specification accompanying drawings inwhich;

Fig. 1 shows one embodiment equipment of my invention.

of the ground" Fig. 2 is a section taken through A-A ,of

Fig. 1. A g v Fig. 3 is a side elevation of Fig. 2. v Fig. 4 is a plan view of one embodiment of th aircraft collector system of my invention.

Fig. 5 is an end elevation of Fig. 4.

Fig. 6 shows schematically one embodiment of the amplifying and indicating aircraft equipment of my invention. I

Fig. '7 shows a conventional type of instrument Fig. .8 depicts zontal coil; Fig. 9 illustrates the connection of a tell-tale .aircraft is completely Fig. 10 illustrates thj: use ,of'a single grounded cable instead of two interconnected cables as in Figs. 1, 2, 8 and 9;

Figs. Hand 12 show difierent coil arrangeconjunction with the to indicate the phase relations are inserted the resistors Point In represents the point at which a landing aircraft should make contact with the earth. I'he altemating current source 3 is connected by means of the cables 4 and 5 to the ends of the cables I and 2 which are .themost remote from point l0.

Fig. 2 represents a section taken through A.A of Fig, 1. 29 is represented 'as being at the heighth above the runway 24 and the cables I and 2' are represented asbeing spaced from the runway by the distance d. It is desirable but not mandatory that the distance it and corresponding distance d at any point .in the runway should be equal.

Fig. 3 shows a side elevation of Fig. 2 taken .through the runway 24. A section 3-3 of Fig. 3 is represented by Fig. 2.

4 "In the preferredmode of operation of my invention,'.the' voltage of the alternating source 3 is adjusted to produce a current flow through 2 cables I and 2 at Section AA of sufilcient value to produce an alternating field having the'value F at a radial distance X from the cables l and 2'; the value F being such that the maximum p0 tential induced in a loop collector moun d in the aircraft will be considerably in excess 0 the potentials induced in the same 'loop' bylocally generated fields surrounding the aircraft. and

the distance X- being the hypotenuse of-the triangle d-7v-:c ofFig'. 2 where h is the desiredheight-oftheaircraft at. the start of the glide path.

In order-toestablish the desired glide aths, the shunting cables 6 are located at such points a and the resistors l are adjusted to such values 5 that the current flowing through the cable I The aircraft carrying loops 28 and and'2 diminishes as a linear or any other desired function of the distance along the cables from the start of the glide path. In. this manner the radial distance X from the cables I and 2 to the point of field strength F is caused to diminish as a linear or any other desired function of the distance along the cables from the start of th glide path.

Having thus established in space a slide p th represented by the locus of the points of constant same manner, should the-aircraft deviate to the right or left of the glide path, the field cutting one of the said loops will increase while the other will decrease thus causing the said pointers to cross at a point to the right or left of the designated center of the said instrument.

Experience has shown that when using the design factors herein described, the magnetic field produced by currents flowing in the ground cables 6 of Fig. 1 is negligibly small in comparison to the magnetic field produced by the currents fiowing in the adjacent sections of cables I and 2.

tion of two loop type collectors 28 and 29 having 2 a plane producing a maximum of induced voltage from one of the ground cables! and 2 and a minimum of induced voltage from the other of said cables.

Fig. 6 is a diagrammatic representation of two amplifiers l5 and iii of conventional design which include substantially linear detectors of conventional design and which are capable of delivering at their output terminals Iii-l9 and 20-2l direct currents which are substantially proportion-- 91 in amplitude to the amplitudes of the voltages applied to their respective input terminals ll-|2 and l3-l4. The instrument I"! of conventional designjcontains two d'Arsonval current indicating instruments of conventional design mounted My invention contemplates, as in Fig. 17, the

use in the aircraft of a conventionalsource llll,

such as a vacuum tube oscillator, 01 a calibrated alternating potential of the same frequency as that supplied to the cables I and 2 by the ground station source 3. By means of conventional switches I02 this said aircraft source will be connected to the input terminals of the amplifiers l5 and IS in place of the loops of Fig. 5 whenever it is desired to calibrate the apparatus of Fig. 6. Calibration of the loops of Fig. 5 will be accomplished at the time of their installation by conventional means.

My invention also contemplates the use of conventional types of bias circuits in connection with the dArsonval instruments contained in instrument l1. Such circuits will permit the use of more sensitive instruments and will therefore provide a more sensitive off-course indication.

A cathode ray tube (Fig. 18) may/tie used to serve the same purpose as the indicating instru ment II. The connection of the pairs of deflection plates I05 and ills of the cathode ray tube to output terminals of the amplifiers l5 and I6,

, and the means I01 and I08 for biasing the cathin such a manner that their respective po nters '22 and 23 intersect or cross, as shown, at the approximate center. of the instrument whenever each pointer is indicating approximately half scale deflection. One d'Arsonval instrument is connected to the output terminals I 3I9 of amplifier l5 and the other said instrument is connected to the output terminals 20-2l of the other amplifier l 6 as shown.

In the preferred mode of operation of my invention-the input terminals lll2 of amplifier l5 and the input terminals l3-il of amplifier it are connecteddirectly to the identically numbered output terminals of the loop type collec-' the aircraft is situated exactly on the desired glide path. It follows from the foregoing description that should the aircraft deviate to a ode ray beam to cause it to be centered within the tube for normal D. C. output of each of said amplifiers are entirely conventional, and will be obvious to anyone skilled in the art.

My invention also contemplates the use of conventional means for indicating the phase relationship between th voltages induced in the two loops as mounted in the aircraft. This phase indicating means may be utilized to indicate whether the aircraft lies within or without the zone bounded by the two vertical projections of cables I and 2. One such phase indicating meansv of conventional designconsists of a relay, de-

picted in Fig. 7, the armature 32 of which is actuated by the moving coil 33 of a dynamome-.

tion of the amplified alternating current obtainable from amplifier l6. Under these conditions, the armature 32 of the dynamometer instrument will contact one of its relay springs 35 whenever point directly above or below the glide path, the

fields cutting-the said loops will decrease or increase respectively by like amounts andthe pointers 22 and 23 will cross at a point respectively above or below the designated center of the instwmentfl'l and thus indicate the position'of the aircraft relative to the glide path. Inth the alternating outputs of the amplifiers l5 and the loops of Fig. 5 have the'opposite phase relation. The relay armature and its springs may I be used, as in Fig. 9, to close the circuit of a pilot light ms to indicate whenever the aircraft is inside the aforesaid zone.

My invention also contemplates the omission of the inter-connecting cables 6 and the substitution of the conducting earth therefof.

Fig. 8 shows another arrangement of coils '28 fed to secure the uniform incremental change in and 29 that, while not so desirable as the apparatus above described, may be used to practice the present invention. In Fig. 8 the coils are'disposed with coil 28 lyingvertically and coil 29 lying horizontally and hence when the loops are in the positions "shown in the figure there will be output current from loop 29 but none from loop 28. However, when the loops are moved laterally from the position shown there will be a change in the output of loop 29 and furthermore there will also be output'from loop 28 having a direction of flow that will depend upon the direction of the lateral movement.

Fig. 10 shows a single conductor 30 disposed.-

along the landing path, grounded at intervals through the resistors 1 to effect a progressive diminution-of the magnetic field strength around the conductor, the return being through earth. Inequalities of current through the several ground connections that might result from differences of conductivity in the ground may be compensated by empirically adjusting the values of the resistors to attain the desired result.

Fig. 11 depicts the use of loops 28 and 29 set at 45 to the horizontal, and Fig. 12 shows loop 29 horizontal and loop 28 vertical, used with the I single grounded conductor 30. In view of the foregoing, it appears unnecessary to discuss in detail the operation of the devices shown in these figures.

Fig. 14 discloses an effective arrangement for mounting the loops 28 and 29 upon an aircraft 40. As shown. in Fig. 13 the loops and 29 are made by taking a cable of suitable length having, for example, twenty conductive wires in a suitable sheath and connecting the ends of the wires in series, leaving the two ends of each coil thus formed to be connected to leads ll, l2 and l3, II, respectively. The loops 28' and 29' are attached to the inside or outside of the fuselage of aircraft 90 with longitudinal side portions M, 92 and 43, M, respectively, so disposed that a plane through the side portions of each loop lies at an angle of "45 to the horizontal, when the airthe magnetic fields.

The following formula is used to determine the voltage induced in each loop collector mounted in the aircraft:

V=384 jINb 10- lo X X Where V=lvlicrovolts induced in each loop.

f=Cycles per second frequency of source 3.

I=.Amperes flowing in cables I point.

N =Number of turns in each loop.

b'=Length in fact of loop sides parallel to earth.

Xa=Radia1 distance in feet from cable to first limb ofloop. Xb=Radial distance in feet from cable I to second limb of loop. Xa'=Radial distance in feetfrom cable 2 to first limb of loop. Xt'=Radial distance in feet from cable 2 to second limb of loop.

As an example of the large values of induced loop voltages obtainable, assume that an aircraft having loops 12 ft. by 4 ft. of 80 turns each, is

located on the glide path at an altitude of 1000' feet andis flying in a levelattitude. Also assume that a 500 cycle current of 5 amperes is flowing through cables I and 2 at a point directly below the aircraft. Considering the loop the' plane of which intersects cable I, it is found that Xa plane is in normal attitude, the ends of the respective loops being designated 45, 46 and 91, 48. It is apparent that this construction will provide loops of'length approximating that of the aircraft, and that these loops may be arranged in any of the positions indicated in other figures of the drawings. w

Fig. 16 shows a further method of producing th magnetic fields of varying strength. Here the,

source 3 of alternating current is adjacent the designated landing point, an. the current flows through a conductor! and a plurality of sec-- tional conductors 2' so arranged as to setup a substantially continuous field, each of the conductors 2' being connected to conductor I through a transformer coil 49 which may be so connected to the next conductor 2' by a tap 50 as to constitute an auto transformer, thereby giving rise to progressively increasing magnetic field strength away from source 3. It is within the purview of my invention to make conductor I also in sections and use transformers having separate primary and secondary coils instead of the auto transformers illustrated, as will be readily apparent'to those skilled in this art. If the distance between successive transformers increases logarithmically, the transformers may all be alike,

otherwise the transformation ratio must be varproduces a change in the magnetic field sur-' equals 1414 feet,'Xb equals 1417 feet'and that Xa'/Xh' equals unity. Upon substituting the foregoing'values in the above formula, it is found that 2600 microvolts are induced in the loop.

. It will -be noted, when the radial distance is large-compared to the radial dimension of the loop, that to a close approximation, the voltage. induced in the loop is inversely proportional to the radial distance'of the loop from the cable.

The invention herein described and claimed may be used and/or manufactured by or for the Government of the United States ofAmerica-forgovernmental purposes without the payment of any royalties thereon or therefor. Iclaim: v 1. An instrument landing system for aircraft,

comprising a pair of electricallyconductive members spaced apart a distance on the order of twice a suitable height to begin a landing glide and lying parallel to each other in a horizontal plane and then convergingtoward a median horizontal lineat an angle substantially on the order of a suitable angle of glide for landing, means to supply alternating current to said members, a plurality of parallel connections between the converging portions of said members each including a resistance at each end and a conductive portion between the resistances, the values of said resistances being so chosen that, the change in current along said members, clue to the current shunted through said connections,

and 2 at any field around each said member, and means actuated by said responsive means to indicate the position of said aircraft path.

5. An instrument landing system for aircraft,

Qpor'nprislng means to set up two like fluctuating twice asuitable height to begin a landing glide I a plurality of parallel connections between the converging portions of said members each including a resistance at each end and a conductive portion between the resistances, the values of said resistances being so chosen that the change in current along said members, due to the current shunted through said connections, produces a change in the magnetic field surrounding each member such that the perpendicular distance from each member to a point of predetermined magnetic field strengthdiminishes along said converging portions so that the locus of said points defines a glide path, and means adapted to be carried aboard an aircraft including means responsive to. the magnetic fields surrounding each of said members, and means actuated by said responsive means to indicate the position of said aircraft with respect to-said glide path.

I 3. An instrument landing system for aircraft, comprising-a pair of electrically conductive members spaced apart a distance on the order of twice a suitable height to begin a landing glide and lying parallel to, each other in a horizontal plane and then converging toward a median horizontal line at an angle substantially on the order of a suitable angle of glide for landing, means to supply alternating current to said members,

magnetic fields symmetrically disposed with respect to a median horizontal line, means to vary progressively the strength of said fields so that the locus of points common to said fields having a predetermined field strength defines a glide path for landing an aircraft, and means adapted to be carried aboard an aircraft including two coils oppositely inclined at angles of substantially to the horizontal, the planes of said coils intersecting in a line'parallel 'to the fore and aft center line of the fuselage, wherein voltages are induced by said magnetic fields, means to amplify said induced voltages, and means actuated by said amplified voltages to indicate the relative positions of said coils with respect to said glide path.

I .6. An instrument landing system for aircraft, comprising a .pair of electrically conductive membersspaced apart a distance on the order of twice a suitable height to begin a landing glide and lying parallel to each other in a horizontal plane and then converging toward a median horizontal line at an angle substantially on the order of a suitable angle of glide for landing,

means to supply alternating current to said,

' members, a plurality of parallel connections parallel cross connections between said converging portions to reduce the current in said members as a function of the: distance from the beginning of said convergence whereby the perpendicular distance from each member to a point I of predetermined magnetic field strength decrease indicate the relative positions of said coils with respect to said glide path.

4. An instrument landing system for aircraft, comprising a pair of electrically conductive members spaced apart a distance on the order of twice a suitable height to begin a landing giideand lying parallel to each other in a horizontal plane and then converging toward a between the converging portions of said members each including a resistance at each end and a conductive portion between the resistances, the

values of said resistances being so chosen that the change in current along said members, due to the current shunted through said connections, produces a change in the magnetic field surrounding each member such that the perpendicular distance from each member to. a point of predetermined magnetic field strength diminishes along said converging portions so that the locus of said points defines a glide median horizontal line at an angle substantially on the order of a suitable angle of glide for landing, means to supply alternating-current to said members, parallel cross connections between said converging portions to reduce the current in said members as a function of the distance from the beginning of said convergence whereby the perpendicular distancefrom each member to a point of predetermined magnetic field strength decreases in accordance with said function, so that the locus of said points defines a glide path, and means adapted ,to'be carried abroad an aircraft including means responsive to the magnetic path and means adapted to be carried aboard an aircraft including separate coil means disposed to be differentially responsive to the magnetic fields around said members and to have electric currents induced therein, and means actuated by said induced currents to indicate the position of said aircraft with respect to said glide path.

7. An instrument landing system for aircraft, comprising means to set up two like flucduced currents to indicate the position of said aircraft with respect to said glide path. I

8. An instrument landing system for aircraft, comprising means to set up two converging fluctuating magnetic fields symmetrical about a median horizontal line and diminishing in strength toward the point of convergence of said fields as a function of the rate of said convergence, and means adapted to be carried aboard an aircraft and having devices responwith respect to said glide V 2,840,282 sive to said fields, and indicating means actuated by said devices to show the position of said i field strength.

9. In an instrument landing system for airlying parallel to each other in a horizontal plane and then converging toward a median'horizontal supply alternating current to said members, a plurality of parallel connections between the converging portions of said members each ineluding a resistance at each end and a conductive portion between the resistances, the values aircraft with respect to the locus of points common to both said fields having a predetermined ated by said induced currents to indicate 'the relative positions of said coils with respect to said glide path.

craft, a pair of electrically conductive members spaced apart a distanceon the order of twice a suitable height to begin a landing glide and line at'an angle substantially on the order of a suitable angle of glide for landing, means to of said resistances being so chosen that the change in current along said members, due to the current shunted through said connections, produces a change in the magnetic field sur- 14. An instrument landing system for aircraft, comprising means to set up two like fluctuating magnetic fields symmetrically disposed with respect to a median horizontal line,

means, to vary progressively the strength of said I fields so that the locus of points, common to said fields having a predetermined-field strength defines av glide path for landing'an aircraft, and

means adapted to be carriedv aboard an aircraft including two coils oppositely inclined at angles of substantially 45 to the horizontal, the planes Of Said coils intersecting in a hne parallel to the fore and aft center line of the fuselage, wherein currents are induced by said magnetic fields, means to amplify said induced currents, means actuated by said amplified currents to indicate the relative positions of said coils with respect to said glide path, and other means actuatedrounding each member such that the -perpen-- dicular distance from each member to a point of predetermined magnetic field strength 'diininishes along said converging portions so that the locus of said points defines a glide path.

10. In an instrument landing system for airnetic fields symmetrically disposed with respect to a median horizontal hue, and ineans to vary progressively the strength of said fields so that the locus of points common to said fields having a predetermined field strength defines a glide path for landing an aircraft.

11..An instrument landing system, comprising a conducting member, a plurality of means each 'including a resistor to ground said member at intervals, said resistors each having such res'pectivevalues that the current in said member decreases as a function of the length of said member, -means to supply alternating current to said member to set up a magnetic field around said member such that the locus of points verti-' cally above said member having a predetermined field strength defines a glide path for landing an. airplane, and means adapted to be carried aboard an aircraft responsive to said magnetic field to indicate the position of said. ,means with respect to said glide path.

12. A piloting system for a moving body, comprising electric circuit means including at least one conducting member extending -toward an objective point to be reached by said body, means to supply alternating current to said circuit means to setup a fluctuating magnetic field craft, means to set up two like fluctuating mag- .on the order or a suitable angle or glide i'or .landing, means to supply alternating current to by said amplified currents to indicate the phase relations or said currents. 7

15. An instrument landing system for aircraft, compris ng a pair of electrically conductive members spaced apart a distance on the order or twice a suitable height to begin a landing glide and lying parallel to each other in a. horizontal plane and then converging toward a median horizontal line at an angle substantially said members, a plurality of parallel connections between the converging portions of said, members each including av resistance at each end and a conductive portion between the resistances, the valuesof said resistances being so chosen that the change in current along said members, due to the current shunted through said connections, produces a change in the mag- ,netic field surrounding each member such that the perpendicular distance from each member to a point of predetermined magnetic field strength diminishes along said converging portions so that the locus of said points defines a glide path, and means adapted to be carried around said means to vary the effective current in said circuit, .means to cause said field to diminish in strength as a function of the length of said circuit, means responsive to said field adapted to be carried aboard said body, and means actuated by said responsive means to indicate the position of said body with respect to said locus.

13. An instrument landing system for aircraft, comprising means to set up two "like flue-- tuating magnetic fields symmetricallydisposed with respect to a median horizontal line, means to vary progressively the strength of said fields so that the locus of points common to said fields having a predetermined field strength defines a glide path for landing an aircraft, and means adapted to be carried aboardan aircraft including a vertically disposed coil and a horizontally disposed coil wherein currents are infields so that the locus of points common to said fields having a predetermined field strength defines a glide path for landing an aircraft, and means adapted to be carried aboard an aircraft including a vertically disposed coil wherein currents are induced by said magnetic fields, and means actuated by said induced currents to indicate the position of said coil with respect to said glide path.

17. An instrument landing system, comprising a conducting member, a plurahty of means each including a resistor to around said member at intervals, said resistors each having such respective values that the current in said mem- H duced by said magnetic fields, and means actuher decreases as a function of the length of said member, means to supply alternating current to said memberto set up a. magnetic field around said member such that the locus 01 points vertically above said member having a predetermined field strength defines a glide path for landing an airplane, a vertically disposed coil,

wherein currents are induced by said field, adapted to be carried aboard an aircraft, and

'means actuated by said induced currents to indicate the position of said coil with respect to said glide path.

18. In combination with an aircraft having a fuselage, an inductive loop mounted -on said fuselage, said loop having longitudinally extending portions on opposite sides of the median longitudinal plane of said craft so disposed that a plane through said portions lies at substantially 45 to the horizontal, and a like loop mounted on said fuselage to lie substantially at right angles to the first-mentioned loop, the planes of said coils intersecting in a line' parallel to the fore and aft center line'of the fuselage.

. 19. Means for producing substantially coextensive elongated magnetic fields varying in strength longitudinally thereof, comprising a conductive member, transformer means connected'to said member at intervals, and means coacting with each of said transformer means to parallel to each other when said indicating' means is not energized, each pointer being connected tobe actuated by the rectified voltage from a respective one of said coils, the circuit values of the connecting means to operate said pointers being so adjusted that each said pointer is moved through an angle of substantially 45 to intersect the other pointer in the ing disposed substantially parallel to the longitudinal axis of an aircraft, with the planes of said coils intersecting in a line parallel to the said longitudinal axis and with the planes of said coils at right angles to each other and at substantially to the horizontal in normal fiightattitude, means to amplify and rectify the voltages induced in each said coil, an indicating means including. two movable pointers predetermined point when said voltages from the two coils are equal and of a selected value, and by the departure of that point of intersection from said predetermined point indicating substantially linearly the direction and magnitude of displacement of said coils from a position in said magnetic field where such induced voltages will be equal and of said selected value.

21. An instrument landing system for aircraft, comprising two coils mounted on the fuselage of a craft and extending substantially the full length of said fuselage, one of said coils extending through the other whereby the effective planes of said coils are at angles of substantially 45 to the vertical longitudinal plane of said craft when in normal flight attitude.

22. An instrument landing system for aircraft, comprising two coils mounted on the fuselage of a craft and extending substantially the full length of said fuselage, one of said coils extending through the other whereby the effective planes of said coils are at angles of substantially 45 'to the vertical longitudinal plane of said craft when in normal fiightattitude and means carried by said craft to indicate the relative values of the voltages induced in said coils stantially 45 to the vertical longitudinal plane of said craft when in normal ,fiight attitude, means carried by said craft to indicatethe relative values of the voltages induced in said-coils by a varying magnetic field and means to indicate the relative phases of' said \induced voltages.

EDWARD N. DINGLEY, JR. 7 

